Aircraft hybrid control box simulation device

Abstract

The utility model discloses an aircraft hybrid control box simulation device, which comprises a long-strip rectangular rear cover shell with a device accommodating cavity, a cover plate and an indication panel which are arranged on the rear cover shell, and an air pressure test switch, a strapdown heading attitude switch, an emergency hydraulic pump switch and a fluorescent bomb release button which are transversely arranged on the front surface of the indication panel side by side, the false touch prevention device is arranged on the indication panel and the cover plate and used for covering the fluorescent bomb release button, the control circuit board is arranged in the device containing cavity, and the interface assembly is arranged on the rear shell cover. According to the utility model, a simulation structure design is carried out by combining operation functions of a hybrid control box MISC of a real machine of a trafficker type, and an electronic circuit structure formed by electronic components such as a two-gear toggle switch and a light touch key switch is mainly adopted to simulate a physical operation structure, so that the operation hand feeling of the real machine and the simplification of devices are realized; the use experience basically indifferent from real machine display and operation is provided for a user, and the manufacturing cost of the device is reduced.

Description

Technical Field

[0001] The utility model relates to a flight simulation device, specifically, to an aircraft hybrid control box simulation device, which is mainly used for simulating the hybrid control box MISC on the left console of the FC-1 fighter jet model. Background Technique

[0002] The FC-1 fighter jet model is one of the well-known classic models, which can provide a simulation operation basis for pilot training and flight enthusiasts to understand and experience the operation of fighter jets. The existing flight simulators are mainly in the form of flight simulation software, and their various operation panels basically adopt virtual buttons on a touch screen, resulting in a poor experience for users. The method of using real aircraft equipment for experience has a high cost and is not suitable for widespread use. On the other hand, there is no dedicated flight simulation device for the FC-1 fighter jet model on the market. Therefore, it is urgent in this field to design a flight simulation device with excellent operation experience and low cost. The hybrid control box is a device on the aircraft that integrates various control functions and usually includes components such as switches, buttons, and indicator lights, which are used to cooperate with the control of various aircraft systems, such as the flight control system, hydraulic system, fuel system, etc. The design of the present utility model is mainly used for simulating the hybrid control box on the left console of the FC-1 fighter jet model. Content of the Utility Model

[0003] Aiming at the problems existing in the above-mentioned prior art, the present utility model provides an aircraft hybrid control box simulation device mainly used for the FC-1 fighter jet model, which realizes the simulation of the hybrid control box on the left console of the FC-1 fighter jet model through a low-cost structural design, facilitating pilot training and flight enthusiasts to experience the operation of fighter jets.

[0004] In order to achieve the above purpose, the technical solution adopted by the present utility model is as follows:

[0005] An aircraft hybrid control box simulation device, comprising a rear cover shell in a long rectangular shape with a device accommodation chamber, a cover plate arranged on the rear cover shell to enclose the device accommodation chamber, an indicator panel attached to the front of the cover plate, four hollow holes arranged side by side and penetrating through the indicator panel and the cover plate for installing components, a pneumatic pressure test switch, a strapdown attitude switch and an emergency hydraulic pump switch arranged side by side horizontally at the right position on the front of the indicator panel, a fluorescent bomb release button arranged at the left position on the front of the indicator panel, an anti-misoperation device arranged on the indicator panel and the cover plate for covering the fluorescent bomb release button, a control circuit board arranged in the device accommodation chamber for carrying and electrically connecting the pneumatic pressure test switch, the strapdown attitude switch, the emergency hydraulic pump switch and the fluorescent bomb release button, and an interface component arranged on the rear cover shell and electrically connected to the control circuit board. Among them, a switch signal acquisition circuit and a data processing module are configured on the control circuit board. The switch signal acquisition circuit is used to collect the input signals of the pneumatic pressure test switch, the strapdown attitude switch, the emergency hydraulic pump switch and the fluorescent bomb release button and transmit them to the data processing module. The interface component is used for power supply and outputting the signals processed by the data processing module to the outside.

[0006] Specifically, the control circuit board is connected to the bottom side of the cover plate through screw bush columns and maintains an installation gap with the cover plate.

[0007] Specifically, the pneumatic pressure test switch, the strapdown attitude switch and the emergency hydraulic pump switch all adopt two-position toggle switches, which are electrically connected to the switch signal acquisition circuit. The toggle lever of the two-position toggle switch extends out of the front of the indicator panel through the hollow hole at its corresponding position.

[0008] Specifically, the fluorescent bomb release button adopts a tactile switch, which is arranged on the control circuit board and electrically connected to the switch signal acquisition circuit. A keycap for facilitating key operation is configured on the tactile switch. The keycap is located in the hollow hole at its corresponding position and is shielded by the anti-misoperation device.

[0009] Specifically, the anti-misoperation device includes an anti-misoperation sleeve ring arranged in the hollow hole corresponding to the fluorescent bomb release button, an anti-misoperation base connected to the bottom of the anti-misoperation sleeve ring and fixedly connected to the cover plate, an operation opening opened on the anti-misoperation base for the fluorescent bomb release button to expose, and a protection cover hinged to one side of the top of the anti-misoperation sleeve ring for shielding the top opening of the anti-misoperation sleeve ring.

[0010] Specifically, the switch signal acquisition circuit uses a register chip with the model number 74HC165 as the core.

[0011] Specifically, the data processing module uses an STM32 development board as the core, and the interface component uses a USB interface or a Type-C interface.

[0012] Specifically, light-transmitting indicating parts are configured at the gear positions and name positions corresponding to the air pressure test switch, strapdown attitude switch, emergency hydraulic pump switch, and flare release button on the indicating panel to indicate the functions of each switch and gear. Backlight LED lights corresponding to the light-transmitting indicating parts are arranged on the control circuit board, and these backlight LED lights are all electrically connected to the data processing module.

[0013] Compared with the prior art, the utility model has the following beneficial effects:

[0014] (1) The utility model designs a simulation structure in combination with the operation functions of the hybrid control box MISC of the FC-1 aircraft. It mainly uses an electronic circuit structure composed of electronic components such as two-position toggle switches and tactile key switches to simulate the physical operation structure, realizing the operation feel of the real machine and simplifying the device components. Cooperating with the switch signal acquisition circuit and the data processing module to collect and process the operation signals of the keys and switches, and combining with the functions of the external flight simulation system, the simulation use of the hybrid control box of the FC-1 aircraft can be effectively realized, thereby providing the user with a usage experience that is basically no different from that of the real machine display and operation, and greatly reducing the manufacturing cost of the device. The utility model is ingeniously designed, simple in structure, low in cost, convenient to use, and suitable for application in flight simulation equipment.

[0015] (2) The utility model uses physical electronic components to physically simulate the functions of the keys and switches on the hybrid control box. Structurally, the combination of the shell and the hollow holes on it ensures the consistency of the device's external shape and appearance with that of the hybrid control box of the FC-1 aircraft, improving the user's immersive experience.

[0016] (3) The utility model is provided with an anti-misoperation device on the flare release button, ensuring the use safety of the flare release button and providing a more realistic operation experience.

[0017] (4) The utility model uses a 74HC165 register chip to realize the signal acquisition of the keys and switches, and uses the STM32 development board as the core of the data processing module, effectively reducing the hardware cost on the basis of ensuring the use performance. At the same time, the USB / Type-C interface is used as the interface for signal transmission and power supply, which can be conveniently and simply connected to other flight simulation equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the external structure of an embodiment of the utility model.

[0019] Figure 2 It is a schematic diagram of the front structure of an embodiment of the utility model.

[0020] Figure 3 It is a schematic diagram of the structure of the indicating panel of an embodiment of the utility model.

[0021] Figure 4 Schematic diagram of the cover plate structure of an embodiment of the present utility model.

[0022] Figure 5 Schematic diagram of the rear cover structure of an embodiment of the present utility model.

[0023] Figure 6 Schematic diagram of the structure of the control circuit board part in an embodiment of the present utility model.

[0024] Figure 7 Exploded view of an embodiment of the present utility model.

[0025] Figure 8 Schematic diagram of the structure of the anti-misoperation device in an embodiment of the present utility model.

[0026] Figure 9 Circuit schematic diagram of a single two-position toggle switch in an embodiment of the present utility model.

[0027] Figure 10 Circuit schematic diagram of a tactile switch in an embodiment of the present utility model.

[0028] Figure 11 Circuit schematic diagram of a register chip in an embodiment of the present utility model.

[0029] Figure 12 Circuit principle interface diagram of the data processing module in an embodiment of the present utility model.

[0030] Figure 13 Circuit schematic diagram of some backlight LED lights in an embodiment of the present utility model. Specific implementation manners

[0031] The present utility model will be further described below in conjunction with the drawings and embodiments. The implementation manners of the present utility model include but are not limited to the following embodiments.

[0032] Embodiment

[0033] As Figures 1 to 13As shown, the aircraft hybrid control box simulation device is mainly used for flight simulation operation of the hybrid control box MISC on the left console of the FC-1 aircraft model. It includes a rear cover shell 1 in the shape of a long rectangle with a device accommodation chamber, a cover plate 2 placed on the rear cover shell to enclose the device accommodation chamber, an indicator panel 3 attached to the front of the cover plate, four hollow holes 4 arranged side by side and penetrating through the indicator panel and the cover plate for installing components, a pneumatic pressure test switch 5, a strapdown attitude switch 6, and an emergency hydraulic pump switch 7 arranged horizontally side by side at the right position on the front of the indicator panel, a flare release button 8 arranged at the left position on the front of the indicator panel, an anti-misoperation device 10 arranged on the indicator panel and the cover plate to cover the flare release button, a control circuit board 9 arranged in the device accommodation chamber for carrying and electrically connecting the pneumatic pressure test switch, the strapdown attitude switch, the emergency hydraulic pump switch, and the flare release button, and an interface component 15 arranged on the rear cover shell and electrically connected to the control circuit board. Among them, a switch signal acquisition circuit and a data processing module are configured on the control circuit board. The switch signal acquisition circuit is used to collect the input signals of the pneumatic pressure test switch, the strapdown attitude switch, the emergency hydraulic pump switch, and the flare release button and transmit them to the data processing module. The interface component is used for power supply and outputting the signals processed by the data processing module to the outside.

[0034] Specifically, the open end of the rear cover shell is provided with an inwardly folded connecting fin 21 for buckling and placing the cover plate. After setting screw holes at corresponding positions on the cover plate, the cover plate and the rear cover shell can be connected and fixed by cap screws 22; an interface opening 23 for exposing the interface component is provided on the side or / and the back of the rear cover shell; according to the installation requirements of the device, a plurality of connection ports 24 convenient for external connection and fixation can also be provided on the back of the rear cover shell. The control circuit board is connected to the bottom side of the cover plate through screw bushings 25 and maintains an installation gap with the cover plate. Both ends of the screw bushings are respectively connected and fixed to the control circuit board and the cover plate by screws. The indicator panel can be fixedly attached to the front of the cover plate by bonding or screw connection. When using screw connection, the connecting screws can be fixed together at the upper end of the screw bushings. Corresponding screw holes or avoidance notches can be set at the positions of the indicator panel corresponding to the cap screws according to the shape requirements. In this embodiment, it is shown in the form of an avoidance notch 26.

[0035] Specifically, the air pressure test switch 5, the strapdown attitude switch 6, and the emergency hydraulic pump switch 7 all adopt two-position toggle switches 16, which are electrically connected to the switch signal acquisition circuit. The toggle lever of the two-position toggle switch extends out of the front of the indicator panel through the hollow holes at its corresponding positions. The two positions of the air pressure test switch correspond to P.H.TEST and AUTO respectively, indicating that the pilot conducts a system test and a system self-check on the air pressure system; the two positions of the strapdown attitude switch correspond to SHARS and OFF respectively, indicating turning on and off the strapdown attitude system; the two positions of the emergency hydraulic pump switch correspond to EMG HYD and OFF respectively, indicating turning on and off the emergency hydraulic pump. As Figure 9 shown is the circuit schematic diagram of a single two-position toggle switch, where the device U34 represents the two-position toggle switch, and the MT-0-102-A101-M200-RS+PJ model can be adopted. The interfaces K106 and K107 are used to connect the corresponding interfaces of the switch signal acquisition circuit.

[0036] Specifically, the flare release button 8 adopts a tactile switch 17, which is placed on the control circuit board and electrically connected to the switch signal acquisition circuit. A keycap for convenient button operation is configured on the tactile switch, and this keycap is located within the hollow hole at its corresponding position and is shielded by the anti-misoperation device 10; through this button, the flares carried on the aircraft can be released, and the flares are usually used to interfere with the enemy's missile tracking system or to transmit emergency signals. As Figure 10 shown is the circuit schematic diagram of the tactile switch, where the device SW29 represents the tactile switch, and the GT-TC152B-H150-L1 model can be adopted. The interface K105 is used to connect the corresponding interface of the switch signal acquisition circuit.

[0037] Specifically, the anti-misoperation device 10 includes an anti-misoperation collar 11 placed within the hollow hole corresponding to the flare release button, an anti-misoperation base 12 connected to the bottom of the anti-misoperation collar and fixedly connected to the cover plate, an operation opening 13 opened on the anti-misoperation base for the flare release button to expose, and a protection cover 14 hinged to one side of the top of the anti-misoperation collar for shielding the top opening of the anti-misoperation collar. When the protection cover is closed, the flare release button cannot be operated, preventing misoperation. When it is necessary to release the flares, first open the protection cover and then operate the button.

[0038] Specifically, the switch signal acquisition circuit uses a register chip of model 74HC165 as the core. One 74HC165 register chip has 8-bit inputs. In this solution, 3 two-position toggle switches and one tactile switch are configured, and only one 74HC165 register chip can be adopted. As Figure 11 shown, where the interfaces K105-K111 are used to connect the corresponding tactile switch and two-position toggle switches, and the interfaces DATA, CLK, and LATCH are used to connect the corresponding interfaces of the data processing module STM32.

[0039] Specifically, the data processing module uses an STM32 development board as the core, and the interface component uses a USB interface or a Type-C interface, which can achieve signal transmission and power supply simultaneously. As Figure 12 shown, the interfaces LATCH, CLK, and DATA are used to connect the switch signal acquisition circuit, the interfaces USBD+ and USBD- are used to connect the interface component for signal transmission, and the interfaces VCC, GND, and 3.3V are used to connect the power supply.

[0040] Specifically, a light-transmitting indicating portion 18 is configured at the corresponding gear positions and name positions of the air pressure test switch, the strapdown attitude switch, the emergency hydraulic pump switch, and the flare release button on the indicating panel, for indicating the functions of each switch and gear. A backlight LED lamp 19 corresponding to the light-transmitting indicating portion is arranged on the control circuit board, and these backlight LED lamps are all electrically connected to the data processing module. As Figure 13 shown is the circuit schematic diagram of the backlight LED lamp. The devices LED97-LED102 represent the corresponding backlight LED lamps, and their on / off states are uniformly controlled by the data processing module through the access to the power supply.

[0041] When the present utility model is in use, it needs to be used in cooperation with corresponding other simulation devices, and a computer installed with flight simulation software needs to be connected for flight simulation training or experience. External power supply and flight simulation software signal data transmission are carried out through the USB or Type-C interface. Operations are performed on the air pressure test switch, the strapdown attitude switch, the emergency hydraulic pump switch, or the flare release button according to the actual requirements of flight simulation operations. The corresponding operation signals are collected by the switch signal circuit and transmitted to the external flight simulation system through the data processing module to achieve corresponding functions. For example: when needed, operate the flare release button to release the flares carried on the aircraft to interfere with the enemy's missile tracking or transmit emergency signals; control the on / off of the aircraft's strapdown attitude system by operating the strapdown attitude switch. The strapdown attitude system is usually used for the attitude control of the aircraft, including pitch, roll, and yaw, etc.; control the on / off of the aircraft's emergency hydraulic pump by operating the emergency hydraulic pump switch. In some cases, the main hydraulic system of the aircraft may fail, and at this time, the emergency hydraulic pump can provide the necessary hydraulic pressure to operate the key systems to ensure the flight safety of the aircraft; test the aircraft's air pressure system by operating the air pressure test switch, which is convenient for the pilot to perform system self-check or test to ensure the normal operation of the air pressure system. The air pressure system is crucial for many aspects of the aircraft, including instruments, start control, and environmental control, etc.

[0042] The hybrid control box is an important part of the flight control system of the FC-1 fighter, which provides control and monitoring functions for various systems of the aircraft to ensure the safety and stability of the aircraft during flight.

[0043] The above embodiments are only the preferred embodiments of the present utility model, and do not limit the protection scope of the present utility model. Any changes made by adopting the design principle of the present utility model and non-creative labor on this basis shall fall within the protection scope of the present utility model.

Claims

1. An aircraft hybrid control box simulation device, characterized in that, It includes a rear cover case in the shape of a long rectangle with a device accommodation chamber, a cover plate placed on the rear cover case to close the device accommodation chamber, an indicator panel attached to the front of the cover plate, four hollow holes arranged side by side and penetrating through the indicator panel and the cover plate for installing components, a barometric pressure test switch, a strapdown attitude and heading reference system (SAHS) switch, and an emergency hydraulic pump switch arranged horizontally side by side at the right position on the front of the indicator panel, a fluorescent flare release button arranged at the left position on the front of the indicator panel, an anti-misoperation device arranged on the indicator panel and the cover plate to cover the fluorescent flare release button, a control circuit board arranged in the device accommodation chamber for carrying and electrically connecting the barometric pressure test switch, the SAHS switch, the emergency hydraulic pump switch, and the fluorescent flare release button, and an interface component arranged on the rear cover case and electrically connected to the control circuit board. Among them, a switch signal acquisition circuit and a data processing module are configured on the control circuit board. The switch signal acquisition circuit is used to acquire the input signals of the barometric pressure test switch, the SAHS switch, the emergency hydraulic pump switch, and the fluorescent flare release button and transmit them to the data processing module. The interface component is used for power supply and outputting the signals processed by the data processing module outward.

2. The aircraft hybrid control box simulation device according to claim 1, wherein, The control circuit board is connected to the bottom side of the cover plate through screw sleeve posts and maintains an installation gap with the cover plate.

3. The aircraft hybrid control box simulation device according to claim 2, characterized in that, The barometric pressure test switch, the SAHS switch, and the emergency hydraulic pump switch all adopt two-position toggle switches and are electrically connected to the switch signal acquisition circuit. The toggle levers of the two-position toggle switches extend out of the front of the indicator panel through the hollow holes at their corresponding positions.

4. The aircraft hybrid control box simulation device according to claim 3, characterized in that, The fluorescent flare release button adopts a tactile switch, is arranged on the control circuit board and is electrically connected to the switch signal acquisition circuit. A keycap for facilitating key operation is configured on the tactile switch. The keycap is located in the hollow hole at its corresponding position and is shielded by the anti-misoperation device.

5. The aircraft hybrid control box simulation device according to claim 4, wherein The anti-misoperation device includes an anti-misoperation collar arranged in the hollow hole corresponding to the fluorescent flare release button, an anti-misoperation base connected to the bottom of the anti-misoperation collar and fixedly connected to the cover plate, an operation opening opened on the anti-misoperation base for the fluorescent flare release button to expose, and a protection cover hinged to one side of the top of the anti-misoperation collar for shielding the top opening of the anti-misoperation collar.

6. The aircraft hybrid control box simulation device according to claim 5, characterized in that The switch signal acquisition circuit uses a register chip with the model number 74HC165 as the core.

7. The aircraft hybrid control box simulation device according to claim 6, characterized in that, The data processing module uses an STM32 development board as the core, and the interface component uses a USB interface or a Type-C interface.

8. The aircraft hybrid control box simulation device according to claim 7, characterized in that Translucent indication parts are configured at the gear positions and name positions corresponding to the barometric pressure test switch, the SAHS switch, the emergency hydraulic pump switch, and the fluorescent flare release button on the indicator panel for indicating the functions of each switch and gear. Backlight LED lights corresponding to the translucent indication parts are arranged on the control circuit board, and these backlight LED lights are all electrically connected to the data processing module.

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